JP2003520937A - Missile intercept missile - Google Patents

Abstract

(57) [Summary] Missile Intercept Missile (10) tracks missiles moving along wake (12) and includes missiles intercepted. The missile (10) has a plurality of projectiles axially packed within the barrel (13) and an independent, selective firing for sequentially propelling the plurality of projectiles through the muzzle of the barrel (13). It includes at least one barrel section (13) with a possible propellant charge. The projectiles create a fragment column (20) along the wake (12) to destroy the attack missile. Alternatively, the missile intercept missile (10) is guided to be a direct hit at point (18) on the offensive missile. The barrel (13) can include an aiming mechanism such that the barrel (13) is rotated through the sectors (15, 16) to target the wake (12).

Description

Detailed Description of the Invention

This invention relates to missile sniper missiles and methods of destroying or disabling attacking missiles.

[0002] Missiles generally move at high speeds towards their targets and are therefore extremely difficult to hit to destroy or incapacitate. While it is possible to deploy multiple defensive munitions from a target to attack an attacking missile, this is undesirable as an initial or sole reaction to the threat. Such attacks of attack missiles are generally more effective the closer they are to the target, so secondary reactions are not allowed if the initial reaction fails to destroy or disable the attack missile. Moreover, if the attacking missile is actually destroyed or incapacitated near the target, it becomes even more of a threat to the target. For example, any destruction of an attack missile near the target will result in an explosion large enough to damage the target and produce fragments of the attack missile with sufficient momentum to damage the target, i.e. Hazardous waste will be scattered.

The early detection of offensive missiles makes it possible to deploy countermeasures in the form of missile deadly missiles. Missile Bombardment Missiles rely on a collision with an attacking missile or an explosion near the attacking missile. The chances of a missile deadly missile successfully colliding with an attack missile are low due to the small size of the attack missile and its relative approaching speed, even with sophisticated aviation and direction control. The missile sniper missile is limited in its ability to make the latest corrections to the flight route according to the latest deviation of the attack missile.

Missile explosive missiles that explode in the vicinity of an attack missile can provide a large number of debris within the wake of the attack missile, or destroy or disable the attack missile when in close proximity. .

The inventor is now able to independently and selectively fire multiple projectiles axially packed within the barrel and sequentially propel the projectiles through the muzzle of the barrel mounted on the missile target missile. By adopting a barrel with both possible launch charges,
We have found that the chances of skillfully destroying or disabling an attacking missile are substantially improved.

[0006] Thus, in one form, the invention provides a missile sniper missile including a missile configured to sniper an attack missile, the missile sniper missile also being axially disposed within at least one barrel. At least one barrel having both a plurality of projectiles packed into the shell and independent and selectively ignitable propellant charge for propelling the plurality of projectiles sequentially through the muzzle of the at least one barrel. Including.

In a second aspect, the invention is a method of destroying or disabling an attack missile, wherein a missile strike missile comprises a missile configured to strike the attack missile, the missile strike A missile also includes a number of projectiles axially packed within at least one barrel and independent selectively ignitable launchers for propelling the projectiles sequentially through the muzzle of the at least one barrel. Providing a method comprising firing a missile sneak-fire missile including at least one barrel having a drug and sequentially firing the plurality of projectiles toward the attack missile.

Attack missiles, such as high altitude ballistic missiles, are widely adopted as long range assault weapons because they are very effective and difficult to find in time to take sufficient defense posture. Has been done. Out-of-atmosphere ballistic missiles move at extremely high speeds and either hit an attack missile directly or rely on a missile that will explode in the immediate missile. Hitting in a hit-to-kill mode is not possible. It's extremely difficult. In one form, the present invention provides missile-hit missiles that improve the likelihood of destroying or disabling extraterrestrial ballistic missiles. The present invention is also directed to destroying or disabling other missiles, including surface-to-air missiles, air-to-ground missiles, air-to-air missiles, surface-to-ground missiles, ship-to-ship missiles, air-to-ship missiles, and other combinations thereof. There are uses. For the exact characteristics of the attack missile,
It is not strictly critical with respect to the definition of the invention.

The missile sniper missile or defensive missile may be of any conventional type capable of sniping an attacking missile. Desirably, the missile deadly missile is capable of colliding with or exploding near the attack missile to destroy or disable the attack missile. Missile Bombardment Missiles are typically
It includes airframes, propulsion systems, guidance systems, and, optionally, explosives that destroy or disable attack missiles.

Missile sniper missiles typically include a guidance system that tracks the trail of an attacking missile and keeps the missile sniper missile, which strikes the attacking missile, on the track. The guidance system may incorporate track sensing means associated with at least one barrel aiming mechanism. The guidance system preferably accommodates advanced aiming corrections made to the barrel for accurately propelling multiple projectiles within the wake of an attack missile. Even if you can't correct the missile target missile track, propelling multiple projectiles into the track increases your chances of disabling the attack missile.

The missile target missile is configured to target an attack missile. The missile deadly missile consists of at least one gun barrel,
Preferably, it is not strictly critical to the invention as long as it can carry at least one barrel that can be rotated to target the wake of an attack missile.

[0012] The missile sniper missile may be launched by any conventional means, such as from a ground-based launch pad, ship, aircraft or otherwise.

[0013] Missile target missiles are multiple projectiles axially packed into at least one barrel and independent selective firing for propelling multiple projectiles sequentially through the muzzle of at least one barrel. At least one with possible propellant charge
Including two barrel parts.

A plurality of projectiles including a barrel and axially disposed within the barrel for operatively sealing engagement with a bore of the barrel, and propelling each projectile sequentially through the muzzle of the barrel. Barrels containing individual propellant charge to cause them to be used in the present invention. Such a barrel portion is disclosed in International Application Nos. PCT / AU94 / 00124 and PCT / AU.
96/00459 and PCT / AU97 / 00713.

The projectile may be machined into a conventional rounded or dart shape with its fins offset to provide a stable spin as the dart is propelled from the barrel, which may be a smooth barrel barrel. The rotation may be generated.

The projectile charge is formed as a solid block that is functionally spaced between the projectiles within the barrel, or the projectile charge contacts prepositioned electrical contacts associated with the barrel. It may be housed in a metal or other rigid case containing an embedded detonator with external contact means adapted accordingly. For example, the detonator allows for the insertion of containerized charge into the barrel and is retracted so that it projects into the barrel opening when aligned with the opening for operative contact with its mating barrel contact. It may also have a spring contact. If desired, the outer case may be disposable or may chemically assist the burning of the charge. In addition, stack-bonded or individually packaged propellant charge and projectile assemblies may be prepared for reloading the barrel.

Each projectile may include a projectile head and expansion means that at least partially define a launch space. The expansion means may include a spacer assembly extending posteriorly from the projectile head and in contact with an adjacent projectile assembly.

The spacer assembly extends through the firing space and the projectile head, thereby transmitting the compressive load directly through the adjacent spacer assemblies in contact. In such a configuration, the spacer assembly may add support to the expansion means, which is the thin cylindrical rear portion of the projectile head. Further, the expansion means may form an operatively sealing contact with the barrel bore to prevent combustion from leaking past the projectile head.

The spacer assembly is in operative sealing contact with the bore of the barrel so that axial compressive loads can be transferred directly between the spacer assemblies, thereby avoiding deformation of the malleable projectile head. It may include a hard collar portion extending outwardly to engage a thin cylindrical rear portion of the un malleable projectile head.

Complementary wedge-shaped surfaces are disposed on the spacer assembly and the projectile head, respectively, such that the projectile head is responsive to relative axial compression between the spacer means and the projectile head. May be biased into engagement with the bore. With this configuration, the projectile head and spacer assembly may be loaded into the barrel and then axially displaced to ensure a sufficient seal between the projectile head and the barrel. . The expansion means is suitably biased to engage the bore of the barrel.

The projectile head defines a tapered opening at its rear end that receives a tapered complementary insert located at the forward end of the spacer assembly, and the projectile head and the tapered complementary insert. Relative axial movement between the parts causes a radial spreading force on the projectile head.

The barrel may be non-metallic and the bore of the barrel may include a recess that fully or partially houses the firing means. In this configuration, the barrel contains a conductor that facilitates electrical conduction between the control means and the firing means. This arrangement may be utilized with a disposable barrel having a firing life limit so that the firing means or control wire or wires may be manufactured integrally with the barrel.

The barrel portion may alternatively include a firing opening in the barrel and the firing means may be located outside the barrel and proximate the opening. The barrel may be surrounded by a non-metal external barrel that includes a recess adapted to accommodate the firing means. The outer barrel may contain a conductor that facilitates electrical conduction between the control means and the firing means. The outer barrel may be formed as a laminated plastic barrel that includes a printed circuit laminate of the firing means.

The barrel portion has adjacent projectiles which are separated from each other and kept spaced apart by positioning means independent of the adjacent projectiles, each projecting body having a barrel bore and a functional seal. An inflatable closure means for forming may be included. The positioning means may be a propellant charge between adjacent projectiles and the closure means suitably includes a skirt portion on each projectile which expands outwardly when subjected to an intra-barrel load. Intra-barrel loading occurs either during loading of the projectile, or after loading such as by packing the projectile and propellant charge columns in order, or as a result of firing an external projectile, especially an adjacent external projectile. .

The posterior end of the projectile is a conical recess into which the propellant charge portion extends and into which the skirt of the projectile expands radially as the projectile moves rearwardly. , Or may include a skirt around an inwardly-reducing recess such as a partially spherical recess. This rearward movement is caused by compression resulting from the rear wedge movement of the projectile along the forward portion of the propellant charge resulting from metal flow from the relatively large and heavy forward portion of the projectile to its small and light skirt.

Alternatively, the projectile may include a rear divergent peripheral sealing flange or collar that deforms outwardly for sealing engagement with the bore during rearward movement of the projectile. In addition, the sealing may be performed by inserting the projectile into a heated barrel that contracts onto each sealed portion of the projectile. The projectile includes a relatively rigid mandrel portion that is positioned by the propellant charge and cooperates with a deformable tubular portion that is molded around the mandrel for sealing engagement with the bore of the barrel. A unitary projectile may be formed that relies on metal flow between the head and tail of the projectile for inflating outwardly around.

The projectile assembly supports a sealing collar portion thereabout and a rearwardly extending anvil adapted to radially expand for sealing engagement with the barrel bore during forward movement of the projectile through the barrel. It may include a surface. In such an arrangement, the propellant charge preferably has a cylindrical front portion that contacts the flat end surface of the projectile.

The projectile may be seated and / or located in the circumferential groove, at the annular rib of the bore, or in the rifling groove of the bore and may include a metal jacket surrounding at least the outer end of the projectile. . The projectile may include a retractable peripheral locating ring that expands outward in an annular groove in the barrel and retracts into the projectile during firing to allow the barrel to pass freely.

The electric ignition device for sequentially igniting the propellant charge in the barrel portion ignites the forward propellant charge by sending an ignition signal through the stacked projectiles, and then the forward propellant charge is ignited. Preferably, the step of preparing the next propellant charge for activation by the firing signal is ready for firing. All propellant charge inward from the end of a properly loaded barrel
The ignition preparatory state is disabled by the insertion of the respective insulating fuzes arranged between the normally closed electrical contacts.

The firing of the propellant charge may be performed electrically, or the firing may be performed by firing the outermost projectile and controlling the resulting firing to sequentially fire the next charge of propellant charge. Conventional firing pin methods may be employed, such as by using a central detonator. This may be done by controlling the back-leakage of combustion gases or by controlling the combustion of fuze rows extending through the projectile.

In another form, firing is electronically controlled with a respective propellant charge associated with a detonator that detonates with a unique firing signal. For example, the detonators in the stacked propellant charge may be arranged in sequence to increase the pulse width firing condition, whereby electronic control selectively sends a firing signal that increases the pulse width and sequentially in a selected time sequence. Ignite the propellant charge. However, preferably, the propellant charge fires at the set pulse width signal, and the combustion of the forward propellant charge prepares the next propellant charge for firing at the next firing pulse.

Suitably in such an embodiment, all propellant charge from the end to the inside of the loaded barrel is secured by the insertion of respective insulated fuzes located between the normally closed electrical contacts, The fuzes are set so that they can burn and close the contact upon transmission of the appropriate firing signal, with each insulated fuze being open to its respective forward firing charge for ignition.

Multiple projectiles can be fired, for example, in unison or in rapid succession, or in response to repeated manual actuation of a trigger. In such a configuration, electrical signals may be sent outside the barrel, or clipped one after another to continue the electrical circuit through the barrel, or via overlapping projectiles that are in electrical contact with each other. You may send it by sending. These projectiles may carry control circuitry or may form circuitry with the barrel.

One or more gun barrels are mounted on the defensive missile, each gun
It may be arranged to scatter, or deploy, fragments both before and after the predicted missile-to-missile collision location within the attack missile wake. Alternatively, a single barrel may be used to propel fragments into and from the predicted missile-to-missile collision location. The barrel may also be fired simultaneously in both directions to minimize changes in the missile wake missile track.

The projectile is preferably a grenade-like projectile capable of exploding in the wake of the attack missile so that the attack missile can build a column of cross section through which it must pass. The likelihood of destroying or disabling an attacking missile is thereby increased.

These or each of the projectiles may be launched from a barbed barrel and use spin counts to measure distance / timing to the flight track. For multiple projectiles fired from barrels of the type described, the spin count is preset for each projectile and the time delay of the firing order is the desired separation of fragments deployed along the flight track. , Or mixed. Alternatively, the timing mechanism may be flight adjustable with appropriate inputs provided by the attack missile track sensing means.

Aiming corrections to the barrel may be done by rotation of the turret about its axis on the defensive missile, even though they may themselves be pivotable about the missile axis. Good. Such a correction is more easily accomplished than the latest deflection of the defense missile flight track. Such aiming corrections are monitored and performed over a relatively long approach period, thereby maintaining a relatively gradual correction operation to achieve accurate firing of the gun or guns.

[0038] The gun barrel or barrels fire projectiles that explode when they enter the desired missile track, scattering fragments, or deploying fragments near the attack missile track, thus providing attack missile and defense capabilities. The missile increases the likelihood of collision with the fragments carried on it. The fragment may have sufficient mass that its collisions at least partially disable the attack missile, or the fragment may be an explosive fragment or explosive. Suitably, the projectile is launched, or deployed, into a wake proximate to the predicted missile-to-missile collision location, thus minimizing the time offset between the launch and fragment deployment or missile-to-missile collision, and Minimize fluctuations in the flight wake of missiles, attack missiles and projectiles.

For any given system, an attack missile having a known velocity, a missile target missile having a known velocity, a barrel having a known muzzle velocity, and an angle at which the barrel is pointed can be of any length. It turns out that the fragment column is constant regardless of where it is needed. This is the direction of the barrel that is offset by 180 degrees,
It is applicable to the fragment column before and after the predicted collision position between the attack missile and the missile target missile. This feature of the invention is that equal and opposite firings are performed to establish a fragment column before and after the predicted collision position of the attack missile with the missile-hit missile with minimal impact on the direction of the missile-hit missile. Sometimes it becomes particularly advantageous.

The methods of defense against attack missiles, as variously described above, form a further aspect of this invention.

In order to more easily understand and practice the present invention, reference is made to the accompanying figures and examples which illustrate exemplary embodiments of the invention. Description of the preferred embodiment

FIG. 1 provides a diagram illustrating a defensive missile 10 traveling along a track 11 that intersects a track 12 of an attack ballistic missile. In this form, tracks 11 and 12 are drawn at right angles for illustration. As shown in FIG. 2, wakes 11 and 12 probably intersect at an obtuse angle of or around 135 degrees.

The protective missiles 10 are each one of the types described above loaded with grenade-type projectiles, each of which engages a rifling groove in each barrel to give the projectile spin when launched. Each projectile is selected from the defensive missile 10 corresponding to the position matching the predicted missile flight trajectory 12 by using the spin count control for firing, as it includes a turret gun 13 with more barrels. Is fired at a certain distance.

The turret gun 13 is used for a considerable distance (eg 300
It may be rotated closer to the line of flight track 11 when firing so that a fragment column from a grenade that explodes along a predicted attack missile flight track 12) on the order of feet can be placed. Alternatively, with the gun still fixed, the different angles required to position the exploding grenade along the flight track may be generated by firing the grenade at different speeds, so the speed of the defense missile,
The velocity of the defensive missile along flight track 11 and the required velocity vector resulting from the missile's launch velocity can be provided, providing results as illustrated by the vectors 15 and 16 and the vectors in between. To achieve.

The flight track of the defense missile 11 is adapted to intercept the flight track 12 of the attacking missile and hit directly at 18 to destroy the attacking missile. However, if this does not occur, damage to the missile incurred by passing through the generated fragment column 20 will prevent the missile from reaching its target value, or will allow it to move naturally while moving towards the target zone. It is enough to disintegrate. In the case of ballistic missiles, this occurs while traveling down through the Earth's atmosphere.

As shown in FIG. 2, the gun is fired in two separate cases. First, in order to generate a fragment column 20 in the wake 12 of the attack missile towards the impact location 18, secondly, the attack missile, after passing beyond the impact location 18 predicted thereby, opposite the impact location. Further fragment columns 21 can be formed in the wake 12 of the.

With reference to FIG. 2, it can be seen that the gun fires prior to being fired to create the leading fragment zone 20, creating a tail fragment zone 21.

As a simple example to illustrate the expected time involved in this, it is believed that a strategic missile traveling at 26,000 feet per second may be shot by a defensive missile traveling at 3,400 feet per second. To be In response to the first firing of the gun to create the tail fragment zone 21, the gun fires in a direction parallel to the flight wake 12 of the attack missile, at a rate of 2,685 feet per second, with a vertical component of 610 feet per second. It is thought that the aim is set to do so. The launch period is also 0.012 seconds in the middle, the projectile is fired, ending 0.559 seconds and 1900 feet in front of impact location 18 and about 300 along the wake 12 of the attack missile beyond impact location 18. It is believed to result in the production of a foot column of fragments.

The gun is then rotated to fire from the other side of the missile-to-missile missile track 11, either by turning the gun 13 or rotating the defensive missile 10 about its axis. The gun then fires forward in a direction parallel to wake 12, at 4,193 feet per second and with a vertical component of 736 feet per second. The launch begins 0.456 seconds and 1,552 feet before impact location 18. The firing period is about 0.012 seconds, and the projectile is fired again, so the attack strategy missile enters the fragment column 20 of about 400 feet in front of the impact position 18 and the next 300 feet of impact before impact. Pass through the fragment column.

This configuration propels a large number of projectiles that explode when they coincide with an attack missile track 12 in a very short period of time, with a firing period of 0.012 seconds being available in this case, a barrel of the described type. Enabled by the use of parts. Further, when the barrel is fully electronically controlled, the electronic configuration can also include adjustable spin count timing means for adjusting in-flight or pre-flight timing to achieve the desired result.

While a single turret gun is preferred for weight savings, individual or multiple guns may be utilized for firing on both sides. In addition, several guns have preset directions and charges, the effective size of the defensive missile to generate an array of fragments around the expected impact zone, and some form of attack missile. It may be deployed around the missile to increase the chance of a collision.

FIG. 3 shows approximate calculations that determine the firing time and firing angle for a particular plan. Here, an attack missile 31 is defined on the x-axis 32 and travels along a trajectory that is predicted to be impacted by a missile sniper missile at 33, and the barrel 3
The launch angles of projectiles (not shown) from 4a and 34b are calculated if the attack angles of the missile target missiles and their respective velocities are known.

E is indicated as the distance along the trajectory of the attack missile that the projectile needs to strike the attack missile. During the time it takes an attack missile to travel a distance e,
Missile target missiles travel a distance c.

[0054]   c = e × (missile target missile speed / attack missile speed) θ is the attack angle of the missile target missile with respect to the direction of the attack missile.

[0055]   a = c × cos (θ−180)

[0056]   b = c × sin (θ-180)

Α = tan ⁻¹ (b / (e + a))

[0058]   β = α + θ-90

Where β is the angle of the barrel with respect to the direction of the missile target missile (applicable to launch after a predicted impact of the attack missile and the missile target missile).

[0060]   γ = 180-β

Where γ is the angle of the barrel relative to the direction of the missile target missile (applicable to launch before the predicted impact of the attack missile and the missile target missile. The target miss time of the projectile with the attack missile ( t _i )

T _i = e / speed of attack missile Flight time of projectile (t _f ).

T _f = d / Velocity of the projectile Firing time of the projectile (t _fire ).

T _fire = t _i −t _f

Based on the equations outlined above, the time and position at which the projectile hits the attack missile was determined, and in Examples 1-8 below, the attack missile, the missile hit missile, and the various speeds, missiles of the projectile The results of these calculations are shown for the attack angle of the sniper missile and the struck position of the projectile with the sniper missile. For convenience, only a few mid-impact points have been selected, but it will be appreciated that the present invention allows a large number of projectiles to be fired in the short period of time in which the launch occurs in close proximity to the attack missile.
It will be appreciated that the closer the launch is to the attack missile, the smaller the margin of error and the greater the chance of destroying or disabling the attack missile.

The preceding description illustrates representative examples of the present invention by way of example, and all modifications and variations thereto will be apparent to those skilled in the art that are obvious to the present invention. It will be appreciated that it is not considered to depart from the spirit and scope.

Example 1 Attack missile speed 7924.8 ms ^-1 Missile target missile speed 1036.32 ms ^-1 Attack angle 220 degrees Projectile launcher Muzzle speed 426.72 ms ^-1

[Table 1]

Example 2 Attack Missile Speed 7924.8 ms ^-1 Missile Target Missile Speed 1676.4 ms ^-1 Attack Angle 220 Degree Projectile Launcher Attack Angle 426.72 ms ^-1

[Table 2]

Example 3 Attack Missile Speed 7924.8 ms ^-1 Missile Target Missile Speed 1036.32 ms ^-1 Attack Angle 190 Degree Projectile Launcher Attack Angle 426.72 ms ^-1

[Table 3]

Example 4 Attack Missile Speed 7924.8 ms ^-1 Missile Target Missile Speed 1036.32 ms ^-1 Attack Angle 220 Degree Projectile Launcher Muzzle Speed 853.44 ms ^-1

[Table 4]

Example 5 Attack Missile Velocity 7924.8 ms ^-1 Missile Target Missile Velocity 1036.32 ms ^-1 Attack Angle 290 Degree Projectile Launcher Muzzle Velocity 426.72 ms ^-1

[Table 5]

Example 6 Attack Missile Speed 7924.8 ms ^-1 Missile Target Missile Speed 1036.32 ms ^-1 Attack Angle 345 Degree Projectile Launcher Muzzle Speed 426.72 ms ^-1

[Table 6]

Example 7 Attack Missile Speed 7924.8 ms ^-1 Missile Target Missile Speed 1036.32 ms ^-1 Attack Angle 220 Degree Projectile Launcher Muzzle Speed 426.72 ms ^-1

[Table 7]

Example 8 Attack Missile Speed 7924.8 ms ^-1 Missile Target Missile Speed 1036.32 ms ^-1 Attack Angle 345 Degree Projectile Launcher Muzzle Speed 426.72 ms ^-1

[Table 8]

[Brief description of drawings]

[Figure 1]   FIG. 1 is a diagram illustrating a typical missile-hit missile and its operation.

[Fig. 2]   FIG. 2 illustrates a typical ballistic analysis.

FIG. 3 illustrates an approximate analysis of ballistics of missiles and projectiles in and out of the atmosphere, respectively.

─────────────────────────────────────────────────── ─── Continued front page    (81) Designated countries EP (AT, BE, CH, CY, DE, DK, ES, FI, FR, GB, GR, IE, I T, LU, MC, NL, PT, SE, TR), OA (BF , BJ, CF, CG, CI, CM, GA, GN, GW, ML, MR, NE, SN, TD, TG), AP (GH, G M, KE, LS, MW, MZ, SD, SL, SZ, TZ , UG, ZW), EA (AM, AZ, BY, KG, KZ, MD, RU, TJ, TM), AE, AG, AL, AM, AT, AU, AZ, BA, BB, BG, BR, BY, B Z, CA, CH, CN, CR, CU, CZ, DE, DK , DM, DZ, EE, ES, FI, GB, GD, GE, GH, GM, HR, HU, ID, IL, IN, IS, J P, KE, KG, KP, KR, KZ, LC, LK, LR , LS, LT, LU, LV, MA, MD, MG, MK, MN, MW, MX, MZ, NO, NZ, PL, PT, R O, RU, SD, SE, SG, SI, SK, SL, TJ , TM, TR, TT, TZ, UA, UG, US, UZ, VN, YU, ZA, ZW

Claims (15)

[Claims] 1. A missile configured to strike an attack missile,
A missile sniper missile, the missile sniper missile also including a number of projectiles axially packed within at least one barrel and a plurality of projectiles sequentially propelled through the muzzle of the at least one barrel. Missile sniper missile, further comprising: at least one barrel having an independent and selectively ignitable propellant charge. 2. The missile sniper missile comprises a guidance system for tracking a track of an attack missile and maintaining the missile sniper missile on the track for slamming the attack missile. Missile Bombardment Missile. 3. The missile-hit missile of claim 2, wherein the guidance system incorporates track sensing means associated with at least one barrel aiming mechanism. 4. The at least one barrel portion, wherein the barrel is a barrel, a plurality of axially disposed projectiles axially disposed within the barrel for operatively sealing engagement with a bore of the barrel, and a barrel muzzle, respectively. Missile-hit missile according to claim 1, characterized in that it comprises a separate launch charge for propelling the projectile of the missile. 5. The projectile is rounded, conventionally shaped, or
Or dart-like, optionally selected from the group consisting of projectiles with fins offset to produce a stable spin rotation when propelled from the barrel. The missile deadly missile according to item 1. 6. The projectile is propelled from at least one barrel by a propellant charge which is sequentially fired by an electronic charge.
Missile target missile described in. 7. The at least one barrel is arranged to deploy a projectile within a wake of an attack missile both before and after a predicted impact of the missile-to-attack missile and the attack missile. The missile-hit missile according to claim 1, wherein: 8. The single barrel portion is arranged to deploy a projectile within the wake of an attack missile both before and after the expected impact of the missile-to-attack missile and the attack missile. The missile-hit missile according to claim 1. 9. The missile sniper missile of claim 1, wherein the gun barrel fires projectiles simultaneously in both directions to minimize any variations in the flight wake of the missile sniper missile. 10. The projectile is a grenade-like projectile capable of exploding in the wake of an attack missile so as to generate a column of fragments that the attack missile must pass through. Missile target missile described in. 11. The method of claim 10, wherein the projectile uses a spin count to measure the distance / timing to a location where it crosses the wake of an attack missile and detonates at that location. Missile target missiles listed. 12. A number of projectiles fired from said at least one barrel have a preset spin count for each projectile and a delay time in firing order is
12. Missile-to-shoot missile according to claim 11, characterized in that it provides a desired separation or mixing of the fragments deployed along the flight track of the attack missile. 13. The timing mechanism of claim 10, wherein flight may be adjustable with inputs provided by an attack missile track sensor.
Missile target missile described in. 14. The aiming correction for at least one barrel may be performed by rotation of a turret about its axis and / or rotation of the missile axis on the missile-hit missile. Missile target missile described in 1. 15. A method of destroying or disabling an attack missile, the missile sniper missile comprising a missile configured to sniper the attack missile axially within at least one barrel. Further comprising at least one barrel portion having both a number of packed projectiles and independent selectively ignitable propellant charge for propelling the plurality of projectiles sequentially through the muzzle of the at least one barrel. A method of destroying or disabling an attack missile, including the step of launching a missile critical missile and sequentially firing the plurality of projectiles at the attack missile.